Abstract:
The existence o f an atmospheric icing th re a t to a irc ra ft operating in moist, low
altitudes at temperatures below freezing is well known.
The objective o f this study was to develop an a irc ra ft ice protection system
suitable fo r a UAV composite wing. Conventional wing leading edge ice
protection systems were examined and found to either, necessitate significant
electrical power, or were costly with respect to system mass.
A low cost and low power technology capable o f protecting the UAV wing leading
edge was identified. I t was proposed th a t a commercial magnetostrictive
actuator fitte d to and in direct contact with the non-airflow wing surface would
provide mechanical impulses to break the ice-wing surface bond.
Assuming the accreted ice was o f a form expected o f te s t points in the FAR/
JAR Appendix C flight-icing envelope. Computational simulations demonstrated
th a t pairs o f magnetostrictive actuators acting in unison a t a 0.3m span spacing,
and deployed along the upper and lower wing leading edge surfaces a t around the
7% chord coordinate, would successfully break the ice-surface bond. I t was
estimated th a t fo r a medium endurance UAV o f Predator B class, the proposed
system power requirements is 500W at a 45kg total system mass.
The proposed system would be more competitive than conventional systems if
the use o f consumer grade electronics and control systems, harnessing etc. were
permitted, together with the removal o f system redundancy and fail-safe
provision requirements necessary fo r manned aircraft.
Further work would require the demonstration o f a physical de-icing installation
in the icing wind tunnel.
